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블레이드 팁의 Groove 형상이 터빈 캐스케이드 팁 열전달 계수분포에 미치는 영향에 대한 실험적 연구
노영철(Young Cheol Nho),조용화(Yong Hwa Jo),이용진(Youn Jin Lee),김학봉(Hark-Bong Kim),곽재수(Jae Su Kwak) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.5
본 연구에서는 팁 형상이 가스터빈 블레이드의 팁 열전달에 미치는 영향을 알아보기 위하여 선형 캐스케이드의 블레이드에 설치된 평면 팁, 스퀼러 팁, Groove 팁들에 대하여 열전달 계수가 측정되었다. 블레이드 팁에서의 열전달 계수는 색상검출방식에 기반을 둔 천이액정법을 이용하여 측정되었으며 각각의 팁 형상에 대하여 팁 간극은 블레이드 스팬의 1.5%와 2.3%로 변경 하에 실험을 수행하였다. 캐스케이드 출구 속도와 블레이드 코드길이에 기초를 둔 Reynolds 수는 2.48×10<SUP>5</SUP> 이다. Groove 팁 표면에서의 열전달 계수는 평면 팁보다 낮게 측정되었으며, 특히 흡입면을 따라 경사진 홈이 파인 팁에서는 스퀼러 팁보다 낮은 열전달 계수가 측정되었다. In this study, the conventional plane tip, double squealer tip, and various groove tip blades were tested in a linear cascade in order to measure the effect of the tip shapes on tip surface heat transfer coefficient distributions. Detailed heat transfer coefficient distributions were measured using a hue-detection based transient liquid crystals technique. Two tip gap clearances of 1.5% and 2.3% of blade span were investigated and the Reynolds number based on cascade exit velocity and chord length was 2.48×10<SUP>5</SUP>. Results showed that the overall heat transfer coefficients on the tip surface with various grooved tips were lower than those with plane tip blade. The overall heat transfer coefficient on grooved along suction side tip was lower than that on the squealer tip.
5공과 7공 프로브를 이용한 터빈 캐스케이드의 이차유동 측정 결과 비교연구
노영철(Young Cheol Nho),이용진(Yong Jin Lee),박정신(Jung Shin Park),서보경(Bo Kyung Seo),김학봉(Hark-Bong Kim),곽재수(Jae Su Kwak) 한국유체기계학회 2009 유체기계 연구개발 발표회 논문집 Vol.2009 No.-
A five-hole and a seven-hole probes were used to measure leakage and passage vortices of a turbine cascade. The experiments were performed at a linear cascade with five blades and three tip gap clearances of 2.3%, 3.1%, and 4.4% of a blade span were tested. The results showed that the leakage vortices measured at tip gap of 3.1% and 4.4% of a blade span have too large flow angle which exceeded the calibration range of the five hole probe. However, seven-hole probe could measure flow angle, total and static pressures at much larger flow angle condition. Using the seven hole probe, we could measure the tip leakage vortex at tip gap of 4.4% of a blade span, which induced strong vortex with large flow angle.
안최란,기효진,진병규,김정균,김석범,조용화,노영철,최용덕,곽재수,최용규,An, Choiran,Ki, Hyojin,Jin, Byeong Kyou,Kim, Jung Kyun,Kim, Sug Bum,Jo, Yong Hwa,Nho, Young Cheol,Choi, Yong Duk,Kwak, Jae Su,Choi, Yong Gyu 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.3
We have fabricated pressure sensitive paint films consisting of PtTFPP activators dispersed in fluorinated polymer matrix. This matrix material is unique in its composition and structure. We evaluated the oxygen quenching effects, and thus the pressure sensitivity, of the fabricated films in terms of various processing parameters. Based on the experimental results, we anticipate that a good but new pressure sensitive paint would be presented through further elaboration of the polymer compositions and optimization of the processing conditions.